Theoretical and Experimental Characterization of Turbulent Heat Transfer in Compressible Flows

Abstract

In this project, we have developed a nano-scale fast thermal anemometry probe to be used in supersonic and hypersonic conditions. The sensor is based on silicon and is manufactured using semiconductor manufacturing techniques. We have characterized how the heat transfer is altered due to the miniaturization and how this can be used to significantly simplify calibration and data analysis. Specifically, it was shown that the relationship between the Nusselt number and the Reynolds number is linear when the sensor is miniaturized, and we have further shown that this is due to slip-conditions. The new sensor was used in a high-speed wind tunnel and compared conventional hot-wires and to Particle Image Velocimetry (PIV).

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Document Details

Document Type
Technical Report
Publication Date
Sep 10, 2019
Accession Number
AD1104528

Entities

People

  • Marcus Hultmark

Organizations

  • Trustees of Princeton University

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Sensors

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Boundary Layer
  • Compressible Flow
  • Computational Fluid Dynamics
  • Flow
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Heat Transfer
  • Hot Wire
  • Hydrodynamics
  • Measurement
  • Reynolds Number
  • Scientific Research
  • Supersonic Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Image Processing and Computer Vision.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Microelectronics
  • Microelectronics - Microelectromechanical Systems